RU2735881C1 - Gas transfer unit - Google Patents

Abstract

FIELD: gas pumping units.

SUBSTANCE: invention relates to gas pumping units with high-temperature gas turbine engines as drives. Invention objective is to increase efficiency of gas turbine engines with high-temperature turbines. Solving said task is achieved in a gas transfer unit comprising a gas turbine engine with a compressor, a combustion chamber and a turbine, free turbine and discharge compressor, fuel system and synthesis gas system, which comprises second gas bleed system and air bleed system due to compressor, ejector-mixer, to which outputs of the second gas bleed system and the air bleed system are connected, to the outlet of the ejector-mixer there connected in series to the first heat exchanger installed in the exhaust device, and a second heat exchanger mounted on the housing of the chamber and a catalyst. At that, the catalyst is installed inside the auxiliary fuel collector, which is made inside the nozzle plate or on it and with additional channels is communicated with air channels of the injector plate.

EFFECT: higher efficiency of gas transfer units with high-temperature turbines.

8 cl, 30 dwg

Description

The invention relates to gas pumping units - GPU with high-temperature gas turbine engines as drives.

Known gas pumping unit using one of the most effective methods to improve the efficiency of the combustion process and improve environmental performance is a method of adding a mixture of hydrogen and carbon monoxide to hydrocarbon fuel, which can be obtained by reforming natural gas in a catalytic reactor of a synthesis gas generator. (Tsybizov Yu.I., Eliseev Yu.S., Fedorchenko D.G. "The use of synthesis gas to ensure the environmental safety of GTU", Aircraft engines of the XXI century, Moscow, TsIAM. P. 461-462.2015).

Disadvantages: Difficulty with heating the feedstock in a catalytic reactor above 600 ° C.

Known gas-pumping unit for the RF patent for invention No. 2708957, IPC F02C 3/00, publ. 12.12.2019, prototype.

This GPU contains a gas turbine engine, a fuel system and a syngas system, which contains a second gas sampling system and an air sampling system due to the compressor, an ejector-mixer, to which the outlets of the second gas sampling system and an air sampling system are connected, to the outlet of the ejector - of the mixer, the first heat exchanger installed in the exhaust device and the second heat exchanger installed on the chamber body and the catalyst are connected in series.

Disadvantage: the relatively low efficiency of synthesis gas as an initiator of the combustion process due to the short lifetime of the radicals formed in the catalyst, which is noticeably far from the nozzles.

The objective of the invention is to improve the efficiency of gas turbine engines with high-temperature turbines.

Achieved technical result: increased efficiency of gas-pumping units with high-temperature turbines.

The solution to this problem has been achieved in a gas compressor unit containing a gas turbine engine with a compressor, a combustion chamber and a turbine, a free turbine and an injection compressor, a fuel system and a synthesis gas system, which contains a second gas extraction system and an air extraction system due to the compressor, an ejector the mixer, to which the outlets of the second gas sampling system and the air sampling system are connected, the first heat exchanger installed in the exhaust device and the second heat exchanger installed on the chamber housing and the catalyst are connected in series to the outlet from the ejector-mixer. In this case, the catalyst is installed inside an auxiliary fuel manifold, which is made inside the nozzle plate or on it, and with additional channels communicated with the air channels of the nozzle plate.

A two-circuit engine can be used as a gas turbine engine.

The drive turbine can be cooled and contains a cooling system for the nozzle apparatus and a rotor with a swirl apparatus and is adjustable.

The drive turbine can be configured to adjust the radial clearance.

The turbine cooling device may contain an "air-to-air" heat exchanger installed in the second circuit, an inlet cavity in front of the swirling apparatus, divided into two identical sectors, to the inlet of each of which a single supply pipeline with a shut-off valve is connected, which is led through the nozzle blades of the blocks using bushings.

The number of nozzle blades in the blocks can be made equal to three, the cavities of the nozzle blades are divided into two: front and rear, the bushings are installed in the middle nozzle blades of the blocks, and a centrifugal compressor is connected to the outlet of the swirl apparatus, located between the turbine disk and the deflector,

Each rotor blade can have two cavities: a front and a rear one, while the openings of the cooling curtain of the leading edge of the rotor blade are brought out into the front cavity.

An "air-to-air" heat exchanger can be installed concentrically with the second heat exchanger through thermal insulation.

The essence of the invention is presented in the drawings. 1 ... 30, where:

- in Fig. 1 shows a diagram of a gas pumping unit,

- in Fig. 2 shows a diagram of a gas pumping unit based on a two-circuit gas turbine engine,

- in Fig. 3 shows a diagram of a combustion chamber and a turbine of a gas turbine unit drive,

- in Fig. 4 shows a diagram of the nozzle plate and the main fuel manifold of the GTE combustion chamber,

- in Fig. 5 shows a nozzle plate with nozzles,

- in Fig. 6 shows a diagram of the fuel supply to the injectors,

- in Fig. 7 shows the design of the nozzle,

- in Fig. 8 shows a section A-A of the nozzle,

- in Fig. 9 shows the nozzle plate in section,

- in Fig. 10 shows a view B of the nozzle plate,

- in Fig. 11 shows graphs of the lifetime of free radicals,

- in Fig. 12 shows an example of a specific implementation of a device for cooling nozzle and rotor blades of a high-pressure turbine of a by-pass gas turbine engine,

- in Fig. 13 shows a diagram of the cooling air supply to the swirling apparatus,

- in Fig. 14 shows a diagram of the supply of cooling air through the blocks of salt apparatus, a swirl apparatus and a centrifugal compressor,

- in Fig. 15 shows a diagram of the supply of cooling air from the sections to the swirling apparatus,

- in Fig. 16 shows the turbine cooling scheme, partial air cut-off,

- in Fig. 17 is a detailed drawing of the drive turbine,

- in Fig. 18 shows a block of nozzle blades left side view,

- in Fig. 19 shows a view C of the block of nozzle blades,

- in Fig. 20 shows a D-D section of a nozzle blade,

- in Fig. 21 shows a section E-E of a nozzle blade,

- in Fig. 22 shows the turbine rotor blade, the first version,

- in Fig. 23 shows the turbine rotor blade, the second version,

- in Fig. 24 shows the design of a centrifugal compressor, section F-F in FIG. 17, first option,

- in Fig. 25 shows the design of a centrifugal compressor, section F-F, the second option,

- in Fig. 26 shows a fragment of the drawing of the impeller,

- in Fig. 27 is a view of G in FIG. 26,

- in Fig. 28 shows a drawing of the sector layout and the supply pipeline, section H-H,

- in Fig. 29 shows the second heat exchanger and the "air-to-air" heat exchanger installed on the combustion chamber housing,

- in Fig. 30 shows a section I-I in FIG. 29.

List of designations used in the description:

1.control unit 1,

2.measurement line 2,

3.measurement controller 3,

4.sensors 4,

5.control line 5,

6.controller 6,

7. actuators 7,

8.Gas turbine engine 8,

9.air cleaning device 9,

10.exhaust device 10,

11.free turbine 11,

12.Compressor shaft 12.

13.power compressor 13,

14.inlet gas pipe 14,

15.outlet gas pipe 15.

16.air path 16,

17.air intake 17,

18.compressor 18,

19.cavity 19.

20.turbine drive 20,

21. gas path 21,

22. combustion chamber 22,

23. camera body 23,

24. Combustion tube 24,

25.nozzle plate 25,

26. fuel-air injector 26,

27. main fuel manifold 27,

28.fuel channels 28,

29. auxiliary fuel manifold 29,

30. auxiliary fuel channel 30,

31. fuel line 31,

32. flow regulator 32,

33. valve 33,

34 syngas system 34,

35 second gas sampling system 35,

36. shut-off valve 36,

37. air bleed system 37,

38. ejector-mixer 38.

39. first heat exchanger 39,

40. second heat exchanger 40,

41.catalyst 41,

42. synthesis gas channel 42,

43. cooling air pipe 43,

44. air-to-air heat exchanger 44,

45 thermal insulation 45,

46 second circuit 46.

47. engine block 47,

48. air manifold 48,

49.nozzle blade 49,

50. external air duct 50,

51.inner air channel 51,

52. first air line 52,

53. first air valve 53,

54 second air line 54,

55 second air valve 55,

56.outlet 56,

57.first inner channel 57,

58.Second inner channel 58,

59. inner air cavity 59,

60.sector 60,

61. partitions 61,

62. axial clearance 62,

63. spinner 63,

64. stator 64,

65. air ducts 65,

66. impeller 66,

67.inner cavity 67,

68. rotor blade 68,

69.Deflector 68,

70. centrifugal compressor 70,

71.blade 71,

72. entrance section 72,

73. inlet edge of the nozzle 73,

74.heat curtain holes 74,

75. turbine flow path 75,

76. block 76,

77. large bandage 77,

78.small bandages 78,

79.Diagonal partition 79,

80.the anterior cavity 80,

81.the back cavity 81,

82. outer holes 82,

83.inner holes 83,

84.front deflector 84,

85.back deflector 85,

Vortex matrix 86,

87 trailing edge 87,

88 exit slit 88,

89. streamlined blades 89,

90. outer seal 90,

91. inner seal 91,

92. hub 92,

93. leading edge of the rotor blade 93,

94. cooling curtain holes 94,

95.shroud shelf 95,

96. seal 96,

97. trailing edge 97,

98.exit slit 98,

99. motor shaft 99,

100. second motor shaft 100,

101.lock 101,

102.Baffle 102,

103. front channel 103,

104.Back channel 104,

105.diffuser 105,

106.Baffles 106,

107.inner wall 107,

108. outer wall 108,

109. gap 109.

110. sensor for measuring radial clearances 110,

111. fins of the second heat exchanger 111,

112. air-to-air heat exchanger fins 112.

α ₀ - angle of installation of streamlined blades,

α ₁ - angle of outflow of cooling air from the swirling apparatus,

β ₀ - angle of installation of the leading edge of the blade,

U - disk rotation speed,

V is the total speed of the cooling air flow,

V ₀ - axial component of the air outflow velocity,

V _u - the circumferential component of the air outflow velocity,

The proposed gas pumping unit - GPA based on a single-circuit gas turbine engine (Fig. 1) contains a control unit 1, measurement lines 2 connecting it to the measurement controller 3 and sensors 4, a control line 5 connecting it to the control controller 6, which is connected to the actuators 7,

The GPU contains a gas turbine engine 8, an air cleaning device 9, an exhaust device 10, a free turbine 11, a compressor shaft 12. an injection compressor 13, an inlet gas pipe 14 connected to the inlet to the injection compressor 13 and an outlet gas pipe 15. connected to the outlet of the injection compressor 13 ...

The gas turbine engine 8 contains an air duct 16, an air intake 17, a compressor 18, a cavity 19 behind it, a turbine, a drive 20, a gas duct 21, a combustion chamber 22.

The combustion chamber 22 contains a chamber body 23, a combustion tube 24, a nozzle plate 25 with fuel-air injectors 26 installed on it, a main fuel manifold 27 connected by fuel channels 28 with fuel-air injectors 26, an auxiliary one is installed inside the nozzle plate 25 or on it. fuel manifold 29 for supplying synthesis gas thereto.

The nozzle plate 25 contains additional fuel channels 30 for supplying the synthesis gas to the fuel-air injectors 26 and mixing it with air (Figs. 1, 2, 8 and 9).

The gas turbine engine 8 includes a fuel line 31, a flow regulator 32 and a valve 33 for supplying fuel.

In addition, it contains a synthesis gas system 34, which contains a second gas sampling system 35 with a second shut-off valve 36 and an air sampling system 37 due to the compressor 18, an ejector-mixer 38, to which the outlets of the second gas sampling system 35 and the system air intake 37. The first heat exchanger 39 installed in the exhaust device 10 and the second heat exchanger 40 installed on the chamber housing 23 and the catalyst 41 are connected in series to the outlet from the ejector-mixer 38. The catalyst 41 is installed inside the auxiliary fuel manifold 29 made on the outer end of the nozzle plate 25, i.e. as close as possible to the fuel-air injectors 26. (Fig. 2 and 3) and is connected to the second heat exchanger 40 by a synthesis gas channel 42.

The installation of the catalyst 41 inside an auxiliary fuel manifold 29 formed inside or a nozzle plate 25, i.e. as close as possible to the fuel-air injectors 26. contributes to the retention of synthesis gas radicals 42.

This is necessary because the retention time of almost all radicals is about 30 nanoseconds (Fig. 11). At a synthesis gas velocity of 100 m / s, almost all radicals recombine after passing 3 cm.

The gas turbine engine 8 (Fig. 2 ... 4) is expediently performed as a high-temperature, double-circuit and with an annular multi-nozzle combustion chamber 22 and with a cooled first drive turbine 20.

The drive turbine 20 includes a cooling air pipeline 43, an air-to-air heat exchanger 44, which is included in the cooling system of the drive turbine 20 and mounted on the second heat exchanger 40 through an insulating gasket 41 in the second circuit 46 under the engine housing 47.

The cooling system includes an air manifold 48 above the nozzle blades 49 of the drive turbine 20.

The combustion chamber 22 comprises an outer air duct 50 and an inner air duct 51 above and below the flame tube 24 (Figs. 3 and 4).

The cooling system of the combustion chamber of the turbine of the drive 20 comprises a first air line 52, a first air valve 53, a second air line 54, and a second air valve 55.

In all, or in part of the nozzle blades 49, there are bushings 56 for supplying cooling air through the nozzle blades 49 to the rotor of the drive turbine 20 (Fig. 3).

To cool the rotor of the turbine of the drive 20, the first inner channel 57 and the second inner channel 58, the internal air cavity 59, divided into sectors 60 by partitions 61 are made. The axial gap 62, the swirling device 63, fixed on the stator 64.

Fuel supply to the combustion chamber of 20 GPU is carried out with gas pumped by the turbopump unit itself.

The main feature of the proposed GPU is the presence of a catalyst 41, laid in an auxiliary fuel manifold 29 on the outer end of the nozzle plate 25, as close as possible to the nozzles 26 to maintain the activity of radicals (Figs. 3, 4 and 11).

To significantly increase the temperature of the gas in front of the drive turbine in order to create an economical gas turbine engine 8, an efficient cooling system of the drive turbine 20 (Figs. 16 and 17) is used, which contains systems for cooling the nozzle blades and the rotor of the drive turbine 20.

For this, air channels 65 are used, made in the impeller 66, the inner cavity 67, the rotor blade 68, the deflector 69, the centrifugal compressor 70, the blade 71, the inlet section 72. The nozzle blades 49 contain the inlet edge of the nozzle apparatus 73, the openings of the heat curtain 74, turbine flow path 75

The nozzle blades 49 are combined into blocks 76 (Fig. 18 ... 21) and have a large shroud 77, a small shroud 78, a diagonal partition 79, a front cavity 80, a rear cavity 81, external and internal holes 82 and 83 (Fig. 20) for cooling blocks of 76 salt blades 49.

External openings 82 connect the external air channel 50 with the cavity of the nozzle blades 49, and the internal openings 83 connect the internal air channel 51 with the cavity of the nozzle blades 49.

To significantly improve the cooling of the nozzle blades 49, a front deflector 84, a rear deflector 85 are installed in them, a vortex matrix 86 is made, and an outlet slot 88 is made in the trailing edge 87 (Fig. 18 ... 21).

The swirl apparatus 63 (FIGS. 12 and 13) contains streamlined blades 89, an outer seal 90, an inner seal 91.

The drive turbine 20 (Fig. 12) contains rotor blades 68 installed on the hub 92 of the impeller 66. The rotor blades 69 contain the leading edges of the rotor blade 93, the cooling curtain holes 94, the shroud 95, the seal 96, the outlet edge 97 and the outlet slot 98 ...

GTE 8 (Fig. 1) has an engine shaft 99, (it is possible to use the second shaft 100 of Fig. 2), lock 101, partition 102, front channel 103, rear channel 104, diffuser 105, partitions 106, inner wall 107, outer wall 108 , radial clearance sensor 110.

The presence of a sensor for measuring the radial clearance 110 allows you to monitor and control the value of the radial clearance in the drive turbine 20.

A feature of the turbine rotor cooling device is that (Fig. 13), the inlet cavity 59 by partitions 61 is divided into sectors 60 of the same size, serving several streamlined blades 89 of the swirl apparatus 63 (Fig. 13).

Recommended number of streamlined blades 89 per sector 60:

n = 3 ... 7.

The first and second internal air ducts 53 and 54 are connected to the entrances to each sector 60 (Figs. 1 and 13 ... 17). The use of such a scheme is justified by the need to maintain without changes in the triangles of the velocities of the outflow of the cooling air from the swirling apparatus 23 when its flow rate changes 2 ... 4 times.The swirling apparatus 63 contains, as mentioned earlier, streamlined blades 89 and is sealed with external and internal seals 90 and 91 (Fig. 3).

The impeller 66 includes a hub 92 to which a motor shaft 99 is attached (FIG. 1).

FIG. 22 shows the first version of the rotor blade 68. It contains the leading edge of the rotor blade 57, the cooling curtain holes 58, the shroud 59, the seal 60, the trailing edge 61, the outlet slot 62. The rotor blade 68 has a lock 101.

FIG. 23 shows the second version of the rotor blade 68. It additionally contains a partition 104, and its internal cavity 67 is divided by a partition 104 into a front channel 105 and a rear channel 196.

FIG. 24 shows the design of a centrifugal compressor 70, the first version, the centrifugal compressor 70 contains blades 71 of a radial shape with inlet sections 72 curved in two planes to reduce the pressure loss of the cooling air at the entrance to the centrifugal compressor 70.

FIG. 25 shows the design of a centrifugal compressor, the second version, the centrifugal compressor 70 contains blades 71 of a curved shape also with inlet sections 72 of a curved shape.

FIG. 26 shows a fragment of the drawing of the impeller 66, it contains under the deflector 69 blades 71 with inlet sections 72, which are curved.

FIG. 27 shows a view A, the entrance portions 72 of a curved shape are visible, and in FIG. 18 shows a drawing of the layout of sector 62 and cooling air pipeline 45. It can be seen that the inlet sections 72 are made at an angle α ₀ = β ₀ , where:

α ₀ - installation angle of streamlined blades 53,

α ₀ - angle of outflow of cooling air from the swirl apparatus 63,

β ₀ - angle of installation of the inlet section 72 of the blade 71.

In the calculations, it is assumed that α ₀ = α ₀ .

With a properly designed turbine cooling system, the condition is met in almost all basic modes;

Cu-U,

those. the circumferential speed of rotation of the disk is equal to the circumferential component of the speed of air outflow practically in the entire range of the GPU.

FIG. 29 shows a diffuser 67, which has inside the baffle 68 in the cooling system of the turbine drive 20 and regulation of the radial clearances to reduce the pressure loss of the cooling air from the sudden expansion of air when entering the internal air cavity 61 through the diffuser 105 with a large diffuser angle, having baffles 106 that reduce diffuser and excluding flow separation from the walls of the diffuser 105.

FIG. 30 shows the design of the "air-to-air" heat exchanger 44.

GPA WORK

The operation of the gas compressor unit (Fig. 1 and 2) is as follows:

When the gas compressor unit is in operation (Fig. 1 ... 30), it is started by supplying electricity to the starter from an external energy source (in Fig. 1 ... 30, the starter is not shown). Then the valve 33 is opened (Fig. 1) and the fuel gas from the outlet gas pipe 15 through the fuel line 31 through the flow regulator 32 is supplied to the main fuel manifold 37 and further to the fuel-air injectors 26 of the combustion chamber 22, where it mixes with the air supplied by the compressor 18 ...

The air required for combustion from the atmosphere enters through the air cleaning device 9 into the air duct 16, then into the compressor 18 into the cavity 19 and into the combustion chamber 22 for use in combustion.

The combustion product from the combustion chamber 22 goes into the turbine 20 and then through the gas duct 21 into the free turbine 11 which drives the injection compressor 13 through the compressor shaft 12 to pump gas.

At the same time, a small gas flow rate is taken from the gas outlet pipe 15 for the syngas system 34 through the second gas sampling system 35 and the shut-off valve 36. For feeding into the injector-mixer 38, where it is mixed with air. High-pressure air is taken from the cavity 19 through the air sampling system 37. The air-gas mixture is first heated to 450 ° C ... 500 ° C in the first heat exchanger 39 installed in the exhaust device 10. Then the air-gas mixture is additionally heated in the second heat exchanger 40. The second heat exchanger 40 is installed on the body of the chamber 23. For modern gas turbine engines, it is possible to heat a mixture of air with gas up to 600 ... 800 ° C required to create synthesis gas, i.e. mixtures containing radicals. For greater efficiency, the synthesis gas is passed through a catalyst 41 mounted in an auxiliary fuel manifold 29.

The auxiliary fuel manifold 29 is installed inside or on the nozzle plate 29 (Fig. 3 ... 10), i.e. as close as possible to the crowd-air nozzles 26. This is necessary in order to keep free radicals (having a short lifetime) before entering the flame tube 24 (Fig. 11).

The presence of a large number of radicals that initiate combustion provides an increase in combustion efficiency and a decrease in the mission of harmful substances.

In circuits using double-circuit. gas turbine engine 8 (Fig. 2) it is possible to use an "air-to-air" heat exchanger 44 to reduce the temperature of the cooling air by 200 ... 300 ° C.

High pressure air (up to 30 ... 40 kgf / cm ² ) is used as cooling air. taken from the cavity 19 behind the compressor 18. This air has a temperature of 450 ° ... 500 ° C and it is expedient to cool it.

The inlet of the air-to-air heat exchanger 44 is connected to the cavity 19. and the outlet is connected to the air manifold 48 installed above the nozzle blades 49 (Fig. 3)

Further, air through the first and second air lines 52 and 54 and air valves 53 and 55 through bushings 56 enters the first and second internal channels 57 and 58 and through the internal air cavity 59 into the swirl unit 63.

From the swirling apparatus 63 it bumplessly enters the centrifugal compressor 70 and through the air channels 65 into the inner cavities 67 of the rotor blades 68 for their cooling ..

Air channels 65 are connected to the internal cavities 67 of the rotor blades 68, which are part of the impeller 66.

The centrifugal compressor 70 is designed to increase the pressure of the cooling air, which is important for curtain cooling. The centrifugal compressor 70 contains blades 71 with inlet portions 72 set at an angle β to the turbine axis RO (Fig. 28).

On the water inlet edges 73 of the rotor blades 68, openings of the thermal curtain 74 are made to communicate with the flow path of the turbine 35 (Fig. 1).

In all modes, the cooling of the nozzle blades 49 is provided by air from the external and internal air channels 50 and 51 through the external and internal openings 82 and 83 of the combustion chamber 22 (Fig. 12).

The supply of cooling air for cooling the turbine drive 20 in the version of the GPU (Fig. 2) is as follows.

With a decrease in engine speed and gas temperature in front of the turbine, on command from the control unit 1 via electrical connections 2 (Fig. 1), the cooling air flow rate is reduced by closing part of the shut-off valves 53 or 55 (Fig. 15). Thus, the flow rate of cooling air in the front and rear channels 102 and 103 of the rotor blades 68 decreases, but increases in the path of the combustion chamber 22, thereby increasing the mass of the working fluid in the turbine. To maintain the engine operating mode, the fuel supply to the combustion chamber 22 is reduced, which lowers the gas temperature in front of the turbine and reduces the specific fuel consumption of the engine, i.e. improves efficiency.

Sensors for measuring radial clearances 110 (Fig. 1) constantly monitor and transmit to the control unit 1 (on-board computer) the value of the radial clearance in the turbine and when it increases above the permissible value (usually when throttling the engine operation mode) due to the fact that the turbine rotor the motor has a higher thermal inertia than the turbine stator

The use of its own shut-off valve 53 and 55 for each sector 60 allows, at low engine operating conditions, to halve the consumption of cooling air, without reducing its pressure and without changing the triangles of the velocities of the outflow of cooling air from the swirling apparatus 63 (Figs. 15 and 28).

FIG. 15 shows the operation of the cooling system when valve 53 is off.

FIG. 28 shows the speed triangles for the proposed turbine cooling system, where:

U - disk rotation speed,

V is the total speed of the cooling air flow,

V ₀ - axial component of the air outflow velocity,

V _u - the circumferential component of the air outflow velocity,

α ₀ - angle of installation of streamlined blades 88 of the swirl apparatus 63,

α ₁ - the angle of outflow of the cooling air flow from the swirl apparatus 63,

β ₀ - angle of installation of the inlet section 72 of the blade 71 of the centrifugal compressor 70.

Considering that approximately:

α ₁ = α ₀ ,

it is proposed to ensure equality of angles at maximum engine operation:

α ₁ = β ₀ ,

where: α ₁ - angle of outflow of cooling air from the swirling apparatus,

β₀ - the angle of installation of the leading edge of the blade, and in other modes provide the closest possible values of the angles α₁ and β₀...

These measures will provide a shockless entry of cooling air into the centrifugal compressor 70 and reduce the air pressure loss in the cooling system of the drive turbine.

The use of the second 40 and air-to-air 44 heat exchangers, combined with the body of the combustion chamber 23 will increase the strength of the body of the chamber 23, reduce the clutter of the second circuit 46 and thereby improve its efficiency and increase the reliability of the engine, eliminating the breakdown of the "air-to-air" heat exchanger 44 due to destruction its walls or tubes from vibration.

The use of blocks 76 of nozzle blades 49 in the amount of 3 pieces in each will make it possible to use the middle nozzle blade 49 of each block 76 to pass through it through bushings 56 to the swirl apparatus 63.

Thus, the invention allows, on the one hand, to ensure the reliability and specified service life of the engine, and, on the other hand, high efficiency in the designs of high-temperature turbines in a wide range of power (revolutions) control of the gas turbine engine.

The cooling system is applicable for the first stages of turbines of modern high-temperature aircraft and marine gas turbine engines.

Application of the invention allowed:

1. To increase the efficiency of the gas pumping unit due to more complete combustion of hydrocarbon fuel, which is achieved by using two heat exchangers for heating the synthesis gas and placing the catalyst in the auxiliary fuel manifold as close as possible to the fuel-air injectors.

2. To reduce the emission of harmful substances into the atmosphere, carbon - C and carbon oxides - CO and nitrogen oxides by increasing the completeness of combustion of fuel gas.

3. Ensure the operability of the GPU during operation at high altitudes (in high mountain areas) through the use of ionized air or ozone.

4. At maximum modes, increase the compression ratio of the gas turbine engine compressor due to the implementation of more complete fuel combustion and increasing the power of the main and free turbines.

Claims (8)

1. A gas compressor unit containing a gas turbine engine with a compressor, a combustion chamber and a turbine, a free turbine and an injection compressor, a fuel system and a synthesis gas system, which contains a second gas sampling system and an air bleed system due to the compressor, an ejector-mixer, to to which the outlets of the second gas sampling system and the air bleeding system are connected, the first heat exchanger installed in the exhaust device, and the second heat exchanger installed on the chamber body, and the catalyst, characterized in that the catalyst is installed inside the auxiliary fuel manifold, are connected in series to the outlet from the ejector-mixer , which is made inside the nozzle plate or on it, and with additional channels communicated with the air channels of the nozzle plate. 2. Gas pumping unit according to claim 1, characterized in that a bypass engine is used as a gas turbine engine. 3. Gas-pumping unit according to claim 2, characterized in that the drive turbine is cooled and contains a cooling system for nozzle devices and a rotor with a swirling device and is made adjustable. 4. Gas pumping unit according to claim 3, characterized in that the drive turbine is configured to adjust the radial clearance. 5. Gas pumping unit according to claim 3, characterized in that the turbine cooling device contains an air-to-air heat exchanger installed in the second circuit, an inlet cavity in front of the swirling apparatus, divided into two identical sectors, to the inlet of each of which one supply pipeline is connected with a shut-off valve, which is passed through the block nozzle blades by means of bushings. 6. The gas pumping unit according to claim 5, characterized in that the number of nozzle blades in the blocks is made equal to three, the cavities of the nozzle blades are divided into two: front and rear, bushings are installed in the middle nozzle blades of the blocks, and a centrifugal one is connected to the outlet of the swirl apparatus. a compressor located between the turbine disc and the deflector. 7. The gas-pumping unit according to claim 5, characterized in that each rotor blade has two cavities: front and rear, while the openings of the cooling curtain of the leading edge of the rotor blade are brought out into the front cavity. 8. Gas pumping unit according to claim 5, characterized in that the "air-to-air" heat exchanger is installed concentrically to the second heat exchanger through thermal insulation.

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